Wing analysis using a transonic potential flow computational method
P. A. Henne, Raymond Morton Hicks, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, McDonnell Douglas Corporation, Ames Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978 - Aerodynamics, Transonic - 55 pages
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0.8 Mach number aerodynamic forces airfoil section angle of attack boundary-layer boundary-layer displacement calculated and experimental Comparison of calculated Comparison of experimental computational method computed and experimental computed results control volume integration displacement thickness distributions for DAC Douglas Aircraft Company drag coefficient drag level drag rise characteristics equation experimental and calculated experimental drag rise experimental results experimental spanwise lift experimental wing pressure figure 18 flow solutions fuselage higher order wall induced drag polars inviscid isentropic flow isentropic shock Jameson code Jameson solution leading edge mesh points NACA NASA nondimensional order wall boundary outboard results shown results were computed section lift coefficient semispan station shock drag characteristics shock waves shown in figure spanwise lift distribution suction peak supercritical supercritical airfoil supercritical wing surface pressure integration sweep theory Swept Wings system shock three-dimensional results trailing edge transonic flow transonic potential flow upper surface velocity wall boundary condition wing geometry wing pressure distributions